한국전산유체공학회지 (Journal of computational fluids engineering)

한국전산유체공학회 (Korean Society of Computational Fluids Engineering)
권호 표지

초음속 역분사 유동이 초음속 비행체 성능에 미치는 영향에 대한 수치해석적 연구

A Numerical Analysis of Supersonic Counter Jet Flow Effect on Performance of a Supersonic Blunt-Body

  • 서덕교 (영남대학교 대학원 기계공학부) ;
  • 서정일 (영남대학교 대학원 기계공학부) ;
  • 송동주 (영남대학교 기계공학부)
  • 발행 : 2002.09.01
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초록

The counter jet flow which is injected against the free stream at stagnation region of blunt body for improvement of aerodynamic performance has been studied by using upwind Navier-Stokes method. The variations of drag force and upwind forward penetration depth due to changes in the stagnation thermodynamic properties of counter jet flow such as total pressure, Mach number, and total temperature have been studied. The results show that the changes in the stagnation pressure and Mach number have large effects on the wall pressure and drag force, but the total temperature does not affect the wall pressure and drag force.

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참고문헌

  1. Ganiev, Y.C. et al., 'Aerodynamic Drag Reduction by Plasma and Hot-Gas Injection,' J. Thermophysics. Heat Trans., Vol. 14, No. 1 (2000), p.10-17
  2. Malmuth, N.D. et al., 'Influence of a Counter Flow Plasma Jet on a Supersonic Bluntbody Pressures,' AIAA Paper No. 4883 (1999)
  3. Lombard, C.K. et al., 'Multi-Dimensional Formulation of CSCM-an Upwind Flux Difference Eigenvector Split Method for the Compressible Navier-Stokes Equa tions,' AIAA-83-1895, (1983)
  4. Kwon, C.O. et al., 'A Computational Studyof Two-Dimensional/Axisymmetric Nonequilibrium Chemistry Reaction Flows Using Upwind Navier-Stokes Method,'CFD J., Vol. 10, No. 1 (2001), p.14-21